Influence of end plates on lift and flow field of a canard-type control surface at a Mach number of 2.00

One of 5,163 reports in the series: NACA Research Memorandums available on this site.

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Description

"The influence of triangular-shaped end plates on the lift and the flow field of a canard-type control surface mounted on a symmetrical fuselage was investigated in the Lewis 8- by 6-foot supersonic wind tunnel at a Mach number of 2.00, body angle of attack of 2 degrees, and control-surface deflection angles of 3 degrees, 6 degrees, 8 degrees, and 10 degrees. The investigation demonstrated that the addition of end plates to a canard-type control surface increased its lift and rearranged the single vortex into a two-vortex system. Perforating the end plates reduced these effects and resulted in a decrease in ... continued below

Physical Description

14 p. : ill.

Creation Information

Wise, George A. March 23, 1953.

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This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and one other and was provided by UNT Libraries Government Documents Department to Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 27 times . More information about this report can be viewed below.

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  • Main Title: Influence of end plates on lift and flow field of a canard-type control surface at a Mach number of 2.00
  • Series Title: NACA Research Memorandums

Description

"The influence of triangular-shaped end plates on the lift and the flow field of a canard-type control surface mounted on a symmetrical fuselage was investigated in the Lewis 8- by 6-foot supersonic wind tunnel at a Mach number of 2.00, body angle of attack of 2 degrees, and control-surface deflection angles of 3 degrees, 6 degrees, 8 degrees, and 10 degrees. The investigation demonstrated that the addition of end plates to a canard-type control surface increased its lift and rearranged the single vortex into a two-vortex system. Perforating the end plates reduced these effects and resulted in a decrease in lift and a change in the flow-field characteristics" (p. 1).

Physical Description

14 p. : ill.

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  • Accession or Local Control No: 93R16727
  • URL: http://hdl.handle.net/2060/19930087437 External Link
  • Report No.: NACA-RM-E53A02
  • Center for AeroSpace Information Number: 19930087437
  • Archival Resource Key: ark:/67531/metadc59495

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National Advisory Committee for Aeronautics Collection

The National Advisory Committee for Aeronautics (NACA) was a U.S. federal agency founded on March 3, 1915 to undertake, promote, and institutionalize aeronautical research. On October 1, 1958 the agency was dissolved, and its assets and personnel transferred to the newly created National Aeronautics and Space Administration (NASA).

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Creation Date

  • March 23, 1953

Added to The UNT Digital Library

  • Nov. 17, 2011, 10:13 p.m.

Description Last Updated

  • May 30, 2018, 12:50 p.m.

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Wise, George A. Influence of end plates on lift and flow field of a canard-type control surface at a Mach number of 2.00, report, March 23, 1953; (digital.library.unt.edu/ark:/67531/metadc59495/: accessed July 21, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.